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United States Patent |
5,583,777
|
Power
|
December 10, 1996
|
Method and apparatus for determining the weight and center of gravity of
a vehicle, particularly an aircraft
Abstract
An apparatus for weighing aircraft, particularly aircraft prior to
take-off, the aircraft having differing undercarriage wheel configurations
(footprints), one to another, the apparatus for use on or in an aircraft
roadway or the like. The apparatus comprises a plurality of spaced apart
wheel load measuring devices and wherein at least the wheel load measuring
devices for the respective main undercarriage wheels are mounted for
lateral movement one to another, and in some cases computer controlled
motorized movement controlled from the aircraft, so that they may be
selectively positioned in spaced relation one to another to suit the
various main undercarriage wheel spacings of the various aircraft to be
weighed. A readout means is operatively linked to the load measuring
devices in order to display the respective wheel loads registered by the
respective load measuring devices. In some cases, a computer is included
for calculating the center of gravity of the respective aircraft. In some
embodiments the nose wheel load measuring device is also mounted for
movement toward and away from the main undercarriage wheel load measuring
devices. Further embodiments disclose a rotatable mounting of the load
measuring devices including controls therefor to facilitate efficient
entry of the aircraft upon the respective load measuring devices. Methods
based on operation of the disclosed apparatus are also disclosed.
Inventors:
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Power; Vivian G. (250 Rivermere Avenue, St. Lambert, Quebec, CA)
|
Appl. No.:
|
177688 |
Filed:
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January 5, 1994 |
Foreign Application Priority Data
| Jan 07, 1993[CA] | 2086891 |
| Jul 07, 1993[WO] | PCT/CA93/00280 |
Current U.S. Class: |
701/124; 73/65.01; 177/199; 702/169; 702/175 |
Intern'l Class: |
G01M 001/12 |
Field of Search: |
364/427,463,567
73/65.01,65.05
177/126,127,134,163,201,202,211,199
|
References Cited
U.S. Patent Documents
2735291 | Feb., 1956 | Quinn | 73/65.
|
2819612 | Jan., 1958 | Borgstrom et al. | 73/65.
|
2932188 | Apr., 1960 | Kennedy | 73/65.
|
4502555 | Mar., 1985 | Gower | 177/25.
|
4639872 | Jan., 1987 | McHale et al. | 364/463.
|
4659274 | Apr., 1987 | France | 414/21.
|
4889202 | Dec., 1989 | Bron | 177/134.
|
4935885 | Jun., 1990 | McHale et al. | 364/567.
|
Foreign Patent Documents |
1248628 | Jan., 1989 | CA.
| |
0153111 | Aug., 1985 | EP.
| |
WO91/14931 | Oct., 1991 | WO.
| |
Other References
Introduction to Photoelectric Sensors, Catalog: Banner Engineering
Corporation pp. 12-21 (date unknown).
Modulated Light Source (MLS) Controls Catalog: Micro Switch, A Honeywell
Division p. E1 (date unknown).
|
Primary Examiner: Chin; Gary
Attorney, Agent or Firm: Fetherstonhaugh & Co.
Parent Case Text
This is a continuation-in-part of application Ser. No. 07/817,040 filed
Jan. 9, 1992 now abandoned.
Claims
The embodiments of the invention in which an exclusive property or
privilege is claimed are defined as follows:
1. An apparatus for weighing aircraft, including aircraft prior to
take-off, the aircraft having differing undercarriage wheel configurations
one to another, the configurations comprising nose or tail wheel and a
pair of spaced apart main undercarriage wheels, the apparatus for use on
or within an aircraft roadway, comprising in combination:
(a) at least one load measuring means for use in weighing the nose or tail
wheel load of the aircraft;
(b) at least one pair of spaced apart load measuring means positioned in
spaced relation to the at least one load measuring means, the at least one
pair of spaced apart load measuring means for use in weighing the
respective main undercarriage wheel loads of the aircraft, the at least
one pair of spaced apart load measuring means being mounted for movement
toward and away from one another in a substantially horizontal plane,
whereby they are positioned relatively one to another to receive the
respective main undercarriage wheels of the aircraft having differing
undercarriage configurations one to another, when the aircraft are moved
upon the apparatus for weighing; and
(c) an aircraft weight readout means operatively linked to the respective
load measuring means for displaying load data measured thereby upon their
receiving and supporting thereon the respective nose or tail and main
undercarriage wheels.
2. An apparatus as defined in claim 1 including controllable motor means
for controllably moving said pair of spaced apart load measuring means
toward and away from one another.
3. An apparatus as defined in claim 2 wherein said motor means comprises
hydraulic motor means.
4. An apparatus as defined in claim 2 wherein said motor means comprises
electric motor means.
5. An apparatus as defined in claim 1 wherein the at least one load
measuring means for use in weighing the nose or tail wheel load is mounted
for movement in a substantially horizontal plane toward or away from the
at least one pair of spaced apart load measuring means, whereby the at
least one load measuring means is positioned relative the pair of spaced
apart load measuring means to receive the nose or tail wheel of the
aircraft having differing undercarriage configurations, when the aircraft
are moved upon the apparatus for weighing.
6. An apparatus as defined in claim 5 including controllable motor means
for controllably moving the at least one load measuring means toward or
away from the at least one pair of spaced apart load measuring means.
7. An apparatus as defined in claim 6 wherein said motor means comprises
hydraulic motor means.
8. An apparatus as defined in claim 6 wherein said motor means comprises
electric motor means.
9. An apparatus as defined in claim 1 wherein the mounting for movement of
the respective spaced apart load measuring means comprises track means for
supporting and guiding movement of the respective spaced apart load
measuring means.
10. An apparatus as defined in claim 5 wherein the mounting for movement of
the at least one load measuring means comprises track means for supporting
and guiding movement of the at least one load measuring means.
11. An apparatus as defined in claim 1 including scale means for use in
positioning the at least one pair of spaced apart load measuring means one
to another.
12. An apparatus as defined in claim 5 including scale means for use in
positioning the at least one load measuring means relative to the at least
one pair of spaced apart load measuring means.
13. An apparatus as defined in claim 9 wherein said track means extends to
comprise a single track for supporting and guiding movement of the
respective spaced apart load measuring means.
14. An apparatus as defined in claim 10 wherein said track means comprises
a single track for supporting and guiding movement of the at least one
load measuring means.
15. An apparatus as defined in claim 14 wherein said single track extends
to interconnect with a single track for supporting and guiding movement of
the respective spaced apart load measuring means.
16. An apparatus as defined in claim 1 wherein the pair of spaced apart
load measuring means comprise low profile flat wheel load weighing means.
17. An apparatus as defined in claim 1 wherein the at least one load
measuring means comprises low profile flat wheel load weighing means.
18. An apparatus as defined in claim 1 including computer means operatively
linked to the respective load measuring means for use in computing said
load data.
19. An apparatus as defined in claim 2 including computer means for use in
controlling operation of said motor means.
20. An apparatus as defined in claim 6 including computer means for use in
controlling operation of said motor means.
21. An apparatus as defined in claim 1 including frame means
interconnecting the at least one load measuring means and the at least one
pair of spaced apart load measuring means, said frame means being mounted
for rotary movement whereby the at least one load measuring means and the
at least one pair of spaced apart load measuring means are rotatable
relative an adjacently positioned aircraft, permitting alignment of the
wheels with the respective load measuring means and the aircraft to be
moved upon the apparatus for weighing.
22. An apparatus as defined in claim 21 wherein said frame means comprises
pivot means positioned intermediate the at least one pair of spaced apart
load measuring means and on an axis passing longitudinally of the at least
one load measuring means, for rotation of said frame means.
23. An apparatus as defined in claim 21 wherein said frame means comprises
pivot means positioned adjacent an end of the at least one load measuring
means remote from the pair of spaced apart load measuring means and on an
axis passing longitudinally of said at least one load measuring means for
rotation of said frame means.
24. An apparatus as defined in claim 22 including motor means for use in
controllably rotating said pivot means.
25. An apparatus as defined in claim 23 including motor means for use in
controllably rotating said pivot means.
26. An apparatus as defined in claim 3 wherein said hydraulic motor means
comprises hydraulic cylinder means.
27. An apparatus as defined in claim 26 wherein said hydraulic cylinder
means is interconnected intermediate the pair of spaced apart load
measuring means.
28. An apparatus as defined in claim 1 including electronic beam
emitter/receiver means for use in interfacing with electronic beam
emitter/receiver means on the aircraft approaching said apparatus to be
weighed, whereby to permit alignment of the aircraft with the apparatus
for aligned reception of the aircraft wheels to be weighed with the
respective load measuring means.
29. An apparatus as defined in claim 21 including electronic beam
emitter/receiver means for use in interfacing with electronic beam
emitter/receiver means on the aircraft approaching the apparatus to be
weighed, whereby to permit said frame means to be moved relative to the
aircraft for aligned reception of said aircraft wheels to be weighed with
the respective load measuring means.
30. An apparatus as defined in claim 22 including electronic beam
emitter/receiver means for use in interfacing with electronic beam
emitter/receiver means on the aircraft approaching the apparatus to be
weighed, whereby to permit said frame means to be moved relative to the
aircraft for aligned reception of the aircraft wheels to be weighed with
the respective load measuring means.
31. An apparatus as defined in claim 23 including electronic beam
emitter/receiver means for use in interfacing with electronic beam
emitter/receiver means on the aircraft approaching the apparatus to be
weighed, whereby to permit said frame means to be moved relative to the
aircraft for aligned reception of the aircraft wheels to be weighed with
the respective load measuring means.
32. An apparatus as defined in claim 1 wherein the at least one pair of
spaced apart load measuring means positioned in spaced relation to the at
least one load measuring means have non-load measuring means attached
thereto for movement therewith.
33. An apparatus as defined in claim 5 wherein the at least one load
measuring means has non-load measuring means attached thereto for movement
therewith.
34. An apparatus as defined in claim 21 wherein said frame means comprises
pivot means for rotatably supporting said frame means together with said
respective load measuring means upon said roadway, between a first
position and a second position, the apparatus including stop means for
limiting rotation of said frame means respective said first and second
positions.
35. An apparatus as defined in claim 34 including motor means operatively
connected to said frame means for use in rotating said frame means
respective said first and second positions, said stop means further
controlling operation of said motor means.
36. An apparatus as defined in claim 1 wherein each of the load measuring
means comprising the pair of spaced apart load measuring means for use in
weighing the respective main undercarriage wheel loads of the aircraft,
comprises a grid means and said grid means comprises a plurality of wheel
load weighing means.
37. An apparatus as defined in claim 36 including controllable motor means
for use in controllably moving said respective grid means relative to the
roadway.
38. An apparatus as defined in claim 37 wherein said motor means comprises
cylinder means positioned vertically below said respective grid means.
39. An apparatus as defined in claim 37 including controllable motor means
for use in controllably moving said respective grid means, relative to the
roadway, in parallel spaced relation one to another.
40. An apparatus as defined in claim 39 wherein said motor means comprises
cylinder means positioned vertically below said respective grid means.
41. An apparatus as defined in claim 1 wherein each of the load measuring
means comprising the pair of spaced apart load measuring means for use in
weighing the respective main undercarriage wheel loads of the aircraft
comprises a support means for a single wheel load weighing means.
42. An apparatus as defined in claim 41 including motor means for use in
controllably moving said respective support means relative to the roadway.
43. An apparatus as defined in claim 42 including motor means for use in
controllably moving said respective support means relative to the roadway
in parallel spaced relation one to another.
44. An apparatus as defined in claim 1 wherein each of the load measuring
means comprising the pair of spaced apart load measuring means for use in
weighing the respective main undercarriage wheel loads of said aircraft,
comprises a grid means and said grid means comprises a single wheel load
weighing means.
45. An apparatus as defined in claim 44 including motor means for use in
controllably moving said respective grid means relative to the roadway.
46. A method for determining the weight of aircraft, including ones having
differing undercarriage wheel configurations one to another, comprising
the steps of:
(a) providing an apparatus mounted on or within a roadway for the aircraft,
the apparatus having at least one load measuring means for use in weighing
the nose or tail wheel load of the aircraft, the apparatus further having
at least one pair of spaced apart load measuring means positioned in
spaced relation to said at least one load measuring means, the at least
one pair of spaced apart load measuring means for use in weighing the
respective main undercarriage wheel loads of the aircraft, the at least
one pair of spaced apart load measuring means being mounted for movement
toward and away from one another in a substantially horizontal plane
whereby they are positioned relatively one to another to receive the
respective main undercarriage wheels of the aircraft when the respective
aircraft are moved upon the apparatus for weighing;
(b) moving the at least one pair of spaced apart load measuring means one
to another in the substantially horizontal plane whereby the main
undercarriage wheels of the aircraft are aligned therewith for receiving
thereon for weighing; and
(c) moving the aircraft upon said wheels upon the roadway toward the
apparatus and thereafter placing the respective wheels thereof upon the
respective load measuring means or moving them thereover, whereby to
permit the weight of the aircraft to be determined.
47. A method as defined in claim 46 including the step of utilizing motor
means to move the at least one pair of spaced apart load measuring means
one to another.
48. A method as defined in claim 47 including the step of utilizing a
computer means to control operation of said motor means to controllably
move the at least one pair of spaced apart load measuring means one to
another.
49. A method as defined in claim 46 including the step of utilizing a scale
means to position the at least one pair of spaced apart load measuring
means one to another whereby the main undercarriage wheels of the aircraft
are received thereon for weighing.
50. A method as defined in claim 46 including the steps of: providing the
at least one load measuring means for use in weighing the nose or tail
wheel load of the respective aircraft with mounting means permitting
movement of the at least one load measuring means toward and away from the
at least one pair of spaced apart load measuring means, whereby the at
least one load measuring means is positioned to receive the nose wheel of
the aircraft when the aircraft are moved upon the apparatus for weighing
and moving the at least one load measuring means relative to the at least
one pair of spaced apart load measuring means whereby to position for
reception of the nose or tail wheel thereon when the aircraft is moved
upon the apparatus for weighing.
51. A method as defined in claim 50 including the step of utilizing motor
means to move the at least one load measuring means relative to the at
least one pair of spaced apart load measuring means.
52. A method as defined in claim 51 including the step of utilizing a
computer means to control operation of said motor means to controllably
move the at least one load measuring means.
53. A method as defined in claim 48 including the step of locating said
computer means on board the aircraft to be weighed.
54. A method as defined in claim 52 including the step of locating said
computer means on board the aircraft to be weighed.
55. A method as defined in claim 48 including the step of programming said
computer means with specification/data relating to the aircraft to be
weighed and accessing from said computer means said specification/data
necessary for use in controlling said operation of said motor means.
56. A method as defined in claim 52 including the step of programming said
computer means with specification/data relating to the aircraft to be
weighed and accessing from said computer means said specification/data
necessary for use in controlling said operation of said motor means.
57. A method for determining the weight of an aircraft comprising the steps
of:
(a) moving the aircraft comprising wheels upon a roadway therefor toward an
apparatus positioned relative the roadway for weighing the aircraft, the
apparatus including a plurality of movably mounted aircraft wheel load
measuring means;
(b) moving the movably mounted aircraft wheel load measuring means
relatively one to another in a substantially horizontal plane whereby to
align for reception wheels of the aircraft when the aircraft is moved upon
the apparatus; and
(c) moving the aircraft upon said wheels upon the roadway toward the
apparatus and thereafter placing the respective wheels thereof upon the
respective load measuring means or moving them thereover whereby to permit
the weight of the aircraft to be determined.
58. A method as defined in claim 46 including the steps of recording the
respective aircraft wheel loads measured by the respective load measuring
means and computing the center of gravity of said aircraft utilizing said
recorded aircraft wheel loads.
59. A method as defined in claim 46 including the steps of providing and
utilizing electronic beam emitter/receiver apparatus to facilitate
reception and alignment of the respective aircraft wheels to be weighed
with the respective load measuring means.
60. A method as defined in claim 59 including the step of controllably
rotating said apparatus upon pivot means mounting the apparatus to the
roadway, to further facilitate alignment of the respective aircraft wheels
to be weighed with the respective load measuring means.
61. A method as defined in claim 60 wherein the step of controllably
rotating occurs generally centrally of the apparatus.
62. A method as defined in claim 60 wherein the step of controllably
rotating occurs generally adjacent a peripheral area of the apparatus.
63. A method as defined in claim 57 including the steps of providing and
utilizing electronic beam emitter/receiver apparatus to facilitate
reception and alignment of the respective aircraft wheels to be weighed
with the respective load measuring means.
64. A method as defined in claim 63 including the step of controllably
rotating the apparatus upon pivot means mounting the apparatus to the
roadway, to further facilitate alignment of the respective aircraft wheels
to be weighed with the respective load measuring means.
65. A method as defined in claim 64 wherein the step of controllably
rotating occurs generally centrally of the apparatus.
66. A method as defined in claim 64 wherein the step of controllably
rotating occurs generally adjacent a peripheral area of the apparatus.
67. A method as defined in claim 57 including the steps of recording the
respective aircraft wheel loads measured by the respective load measuring
means and computing the center of gravity of the aircraft utilizing said
recorded aircraft wheel loads.
Description
BACKGROUND OF THE INVENTION
(1) Field of the Invention
The present invention relates to methods and apparatus for determining the
weight and the location of the center of gravity of a vehicle,
particularly aircraft, and particularly aircraft prior to their taking
off.
(2) Description of the Prior Art
Methods and apparatus for use in determining the weight and the location of
the center of gravity of an aircraft are known. Such include those
disclosed in U.S. Pat. No. 4,639,872 dated Jan. 27, 1987 to McHale et al.
and U.S. Pat. No. 4,935,885 dated Jun. 19, 1990 to McHale et al. Some
embodiments disclosed in the more recent '885 reference require the use of
a large number of relatively expensive load measuring means. Furthermore,
the embodiments disclosed require aircraft to be weighed, to be
considerably maneuvered in order to enter upon the weighing apparatus.
Confinement of space may in some cases inhibit such maneuvering to take
place or at least make maneuvering of the aircraft difficult.
SUMMARY OF THE INVENTION
It is therefore an important aim of the present invention to provide
improved methods and apparatus to those known for use in determining the
weight and the location of center of gravity of aircraft and which
overcome the aforementioned disadvantages. Further, to address the
aforementioned problem of maneuvering.
In one aspect of the present invention there is provided an apparatus for
weighing aircraft, including aircraft prior to take off, the aircraft
having differing undercarriage wheel configurations one to another, the
configurations comprising nose or tail wheel and a pair of spaced apart
main undercarriage wheels, the apparatus for use on or within an aircraft
roadway, comprising in combination: (a) at least one load measuring device
for use in weighing the nose or tail wheel load of the aircraft; (b) at
least one pair of spaced apart load measuring devices positioned in spaced
relation to the at least one load measuring device, the at least one pair
of spaced apart load measuring devices for use in weighing the respective
main undercarriage wheel loads of the aircraft, the at least one pair of
spaced apart load measuring devices being mounted for movement toward and
away from one another in a substantially horizontal plane, whereby they
are positioned relatively one to another to receive the respective main
undercarriage wheels of the aircraft having differing undercarriage
configurations one to another, when the aircraft are moved upon the
apparatus for weighing; and (c) an aircraft weight readout device
operatively linked to the respective load measuring devices for displaying
load data measured thereby upon their receiving and supporting thereon the
respective nose or tail and main undercarriage wheels.
In a further aspect of the present invention there is provided a method for
determining the weight of aircraft, including ones having differing
undercarriage wheel configuration one to another, comprising the steps of:
(a) providing an apparatus mounted on or within a roadway for the
aircraft, the apparatus having at least one load measuring device for use
in weighing the nose or tail wheel load of the aircraft, the apparatus
further having at least one pair of spaced apart load measuring devices
positioned in spaced relation to the at least one load measuring device,
the at least one pair of spaced apart load measuring devices for use in
weighing the respective main undercarriage wheel loads of the aircraft,
the at least one pair of spaced apart load measuring devices being mounted
for movement toward and away from one another in a substantially
horizontal plane whereby they are positioned relatively one to another to
receive the respective main undercarriage wheels of the aircraft when the
respective aircraft are moved upon the apparatus for weighing; (b) moving
the at least one pair of spaced apart load measuring devices one to
another in the substantially horizontal plane whereby the main
undercarriage wheels of the aircraft are aligned therewith for receiving
thereon for weighing; and (c) moving the aircraft upon said wheels upon
the roadway toward the apparatus and thereafter placing the respective
wheels thereof upon the respective load measuring devices or moving them
thereover, whereby to permit the weight of the aircraft to be determined.
In a further aspect of the present invention there is provided a method for
determining the weight of an aircraft comprising the steps of: (a) moving
the aircraft comprising wheels upon a roadway therefor toward an apparatus
positioned relative the roadway for weighing the aircraft, the apparatus
including a plurality of movably mounted aircraft wheel load measuring
devices; and (b) moving the movably mounted aircraft wheel load measuring
devices relatively one to another in a substantially horizontal plane
whereby to align for reception wheels of the aircraft when the aircraft is
moved upon the apparatus; and (c) moving the aircraft upon its wheels upon
the roadway toward the apparatus and thereafter placing the respective
wheels thereof upon the respective load measuring devices, or moving them
thereover, whereby to permit the weight of the aircraft to be determined.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention is illustrated by way of example in the accompanying drawings
wherein:
FIG. 1 is a diagrammatic plan view of an apparatus in accordance with the
present invention;
FIG. 2 is a diagrammatic part elevational view of the apparatus shown in
FIG. 1 including some additional features;
FIG. 3 is a diagrammatic plan view of a further apparatus in accordance
with the present invention;
FIG. 4 is a diagrammatic plan view of a further apparatus in accordance
with the present invention; and
FIG. 4A is a diagrammatic plan view of an apparatus similar to that shown
in FIG. 4 except showing additional optional features.
DESCRIPTION OF PREFERRED EMBODIMENTS
Referring to FIG. 1 there is shown an arrangement 100 comprising apparatus
for weighing aircraft which comprise differing undercarriage wheel
configurations one to another, such configurations comprising nose and/or
tail wheels and spaced apart main undercarriage wheels. Apparatus 100,
like others disclosed herein, are capable, as well be evident from the
description hereinafter, of weighing such aforementioned aircraft
regardless of the spacing(s) differences of their undercarriage wheels one
to another. Importantly, apparatus 100, like others disclosed herein, may
be installed at various locations such as for example an airport gate,
taxi way, runway threshold, or within aircraft hangars wherein they will
find various uses. Apparatus 100 and others disclosed herein may be
conveniently installed upon or within the aircraft roadway or the like
using suitable well known means.
Referring again to FIG. 1 there is seen one load measuring means 10 for use
in weighing the nose or tail wheel load of an aircraft when placed upon
arrangement 100. Spaced from load measuring means 10 are a pair of spaced
apart load measuring means 11 and 12 for use in weighing the respective
main undercarriage wheel loads of an aircraft. Load measuring means 10, 11
and 12 in the case of arrangement 100 are all mounted for movement
respectively one to another. Load measuring means 10 may be selectively
moved along axis A toward and away from axis B along which load measuring
means 11 and 12 are moved, load measuring means 11 and 12 being movable
toward and away from one another whereby to align with and correctly
receive the main undercarriage wheels of the aircraft to be weighed. Thus
it will be understood load measuring means 11 and 12 are moved apart to
suit the spacing between the main undercarriage wheels of the aircraft to
be weighed. Likewise, load measuring means 10 is positioned along axis A
to suit the spacing between the nose or tail wheel and axis B representing
the axis of the main undercarriage wheels of the aircraft to be weighed.
All necessary wiring, which may comprise fiberoptics, for the various
components, as in the case of other embodiments, may be installed using
conventional methods.
Load measuring means 10, 11 and 12, which are of the well known low profile
type manufactured for example by General Electrodynamics Corp. of Dallas,
Tex., may be mounted for movement in a number of ways. In the case of
arrangement 100 they are slidably moved on wheels (not shown) along their
respective axes A and B. In the one preferred embodiment arrangement 100,
load measuring means 11 and 12 are interconnected to hydraulic means, i.e.
to rigidly mounted hydraulic cylinder 13 having a pair of pistons (not
shown) whose movable rods 14 and 15 are interconnected respectively to
load measuring means 11 and 12. As will be evident rods 14 and 15 are
selectively extended from or retracted within cylinder 13 to selectively
position load measuring means 11 and 12 respective one another. An
alternative hydraulic arrangement is also shown in FIG. 2 utilizing a
hydraulic cylinder 16, which may be pivotally mounted to a rigid wall or
other structure as shown.
In the case where the nose or tail or spaced main undercarriage wheels each
comprise a number of wheels, including bogey wheel arrangements,
additional movably mounted load measuring means of the 10, 11 and 12 type
may be required. An example of additional load measuring means are
represented by the dotted line areas 17, 18 and 19 best seen in FIG. 1.
Load measuring means 17, 18 and 19 may for example be interconnected to
and moved respectively by a pivotally mounted hydraulic cylinder 16,
typically shown in FIG. 2. The terms main undercarriage, nose and tail
wheel used in the specification may also refer to for example bogey
wheels, i.e. more than one wheel.
Alternatively, load measuring means 10, 11, 12, 17, 18 and 19 may be moved
along their respective axial paths using alternative hydraulic motor means
or suitable electric motor means designated M1 in FIG. 2. The various load
measuring means employed may or may not be supported on track-like frame
means, an example of which is shown and designated in FIG. 1 by numerals
20, 21 and 22, upon which the aforementioned wheels (not shown) run.
Track-like frame means 20, 21 and 22, which comprise rails, may if desired
be interconnected one to another as for example shown by dotted lines in
FIG. 1. This is particularly convenient where the collective load
measuring means of arrangement 100 are to be rotated upon a pivot means,
as discussed in detail hereinafter, for such track-like frame means
interconnection provides, in some instances, a mounting structure for the
pivot means. However, the latter is an optional feature as will be
appreciated from the following description.
In the case of the more simple embodiments, the aforementioned load
measuring means are manually moved along the respective axes A and B, and
to aid correct positioning of the load measuring means one to another for
the respective differing undercarriage wheel spacings, a scale means C, D
and E may be used. Alternative means for correctly positioning the
respective load measuring means, including computer controlled operation,
is discussed hereinafter.
As will be understood, the aircraft wheel engaging surface of the
respective load measuring means may be flush with the roadway surface
accessing the aircraft to arrangement 100 and the others discussed.
Alternatively, conventional ramping intermediate said wheel engaging
surface and roadway surface may be used, such being convenient in some of
the rotatable weighing arrangements. As will be understood, the
aforementioned scale means may where convenient be marked in terms of
aircraft model numbers rather than applicable dimensional figures, for
easy reference.
Attention is again directed to FIG. 1 wherein a non-load measuring
means/plate-like means 23 is shown. Plate-like means 23 is linked in
tandem arrangement to load measuring means 10 for rolling movement
therewith. If necessary, additional plate-like means 23 may be linked to
load measuring means 10, i.e. intermediate load measuring means 10 and 19,
the purpose of the non-load measuring means being to provide continuity of
aircraft wheel support surface with the load measuring means, to avoid the
possibility of rolling damage to the aircraft wheels. As will be
understood, as load measuring means 10 is moved toward load measuring
means 11 and 12, non-load measuring means 23 having edge 23', which
preferably comprises wheel ramping means 23", merely slides upon its wheel
mounting, and may if necessary pass between track-like frame means 20 and
21. As indicated, load measuring means 11, 12, 17 and 18 may comprise
ramping means similar to ramping means 23". The length of non-load
measuring means 23 is of course determined by the track length required
when load measuring means 10 is positioned at maximum distance away from
load measuring means 11, 12, 17 and 18.
Attention is directed to FIG. 3 and arrangement 200 wherein it will be seen
an alternative non-movably mounted load measuring means 10' for the nose
or tail wheel is used in conjunction with movably mounted load measuring
means 11, 12 and possibly 17 and 18 for the main undercarriage wheels. As
will be appreciated, it is optional whether to utilize a non-load
measuring means such as item 23 with load measuring means 11, 12, 17 and
18, taking into account the main undercarriage wheels will be received by
the prior positioned load measuring means 11, 12, 17 and 18. As will be
understood, the use of such non-load measuring means would ensure
continuity of wheel rolling surface for other vehicles such as service
vehicles passing over arrangements 100 and 200. As may be appreciated,
exercising the latter option to use non-load measuring means 23 in the
case of embodiments having track-like frame means placed within the
roadway will result in more elaborate arrangements in providing continuity
of wheel supporting surface. One such more elaborate example would involve
the sliding of non-load measuring means 23 just under the aircraft wheel
roadway surface.
As indicated previously, track-like frame means 20 and 21 may be
interconnected to form a single track for the rolling support of the
respective load measuring means 11, 12, 17 and 18. This is represented by
the dotted lines shown in FIG. 3.
As also indicated previously, arrangements 100 and 200 may comprise a pivot
mounting means for use in rotatably supporting, collectively the various
load measuring means. Two examples of such pivotal mountings are shown in
FIG. 1. In the first example, track-like frame means 20, 21 and 22 are
extended as indicated by the dotted lines to provide attachment for a
pivot means P1 which is controllably rotated by motor means M4, which may
comprise any suitable known type. Controlled operation of motor means M4
thus controllably rotates load measuring means 10, 11 and 12 (and if
present load measuring means 17, 18 and 19) about pivot means P1 to
provide or aid aligned paths of reception for the respective nose or tail
and main undercarriage wheels of an aircraft approaching arrangements 100
or 200 to be weighed. Pivoting of the weighing apparatus accordingly
avoids having to otherwise much maneuver the aircraft in order for it to
properly enter upon the apparatus, i.e., its respective wheels are
properly received upon load measuring means 10, 11 and 12 (and load
measuring means 17, 18 and 19 when required).
In the second example, track-like frame means 20, 21 and 22 are extended as
shown by dotted lines in FIG. 1 not to provide a pivot mounting as
discussed above but to provide a T-like frame configuration comprising
track-like frame means 20, 21 and 22 having the pivot means P2, rotation
of which is controlled by motor means M3. Such pivot means permits a
pendulum-like movement of the composite load measuring means 10, 11 and 12
(17, 18 and 19). As in the case of the first example, well known caster
means (not shown) may be employed to assist rolling support of the
plurality of track-like frame means. The benefits of utilizing pivot means
P2 are similar to those discussed above with respect to pivot means P1.
A further alternative to the aforediscussed pivoting arrangements is to
provide, for an "in-ground" installation, a turntable type mounting
wherein portions of the roadway or the like are also rotated about pivot
means position P1. The peripheral edge of such a turntable arrangement is
indicated by phantom line X in FIG. 1. Controlled rotation of the
turntable arrangement may be carried out by motor means, for example motor
means M4 or alternatively by motor means M2 located adjacent peripheral
edge X, suitably installed using well known gear drive means.
From the foregoing it is seen various pivoting designs of the aircraft
weighing apparatus arrangements 100 and 200 may be provided to facilitate
efficient entry of the aircraft wheels to be weighed upon the apparatus.
As will be evident, in many instances limited rotation of the weighing
apparatus is required, i.e., rotation through a selected radial arc. To
provide such limited rotation, a pair of stop means may be utilized. Such
may be used for both manual or motorized limited rotation of the weighing
apparatus arrangements 100 and 200. The stop means may for example
comprise abutments 24 and 25 on for example track-like frame means 20 and
21 for engaging respective fixed abutments 24' and 25', when pivot P1 is
used. Alternatively, the stop means may comprise abutments 26 and 27 on
for example opposing sides of track-like frame means 22 for engaging
respective fixed abutments 26' and 27', when pivot P2 is used. Stop means
of the type discussed may also be applied to the aforementioned turntable
type mounting. Such may comprise abutments 28 and 29 on the turntable T
for engaging respective fixed abutments 28' and 29'.
The present invention provides for efficient entry of the aircraft wheels
to be weighed upon the apparatus, such comprising electronic beam emitter
and receiver means. These elements permit the aircraft to efficiently and
correctly maneuvered respective the weighing apparatus, also the weighing
apparatus to be efficiently and correctly positioned relative the aircraft
to be weighed.
Attention is once again directed to FIG. 1 wherein there is seen a first
electronic beam emitter/receiver E1 located on axis A adjacent the
terminal end of track-like frame means 22. Spaced therefrom on axis A
adjacent the free end of non-load measuring means 23 is a second
electronic beam emitter/receiver E2. Further electronic beam
emitter/receivers E3 and E4 are seen positioned on the longitudinal center
line respectively of load measuring means 11 and 12. The aforementioned
respective beam emitters emit linear pencil-like beams for interfacing
with transponders or the like on the aircraft to be weighed or
alternatively the aforementioned respective beam receivers receive linear
pencil-like beams emitted from emitters on the aircraft to be weighed.
Operation of the electronic beam devices which may be of any suitable
type, including photo electric equipment comprising fiberoptics
manufactured for example by Microswitch Division of Honeywell, is
described below. Useful references in this art are also provided by Banner
Engineering Corporation of Minneapolis, Minn. The term "electronic beam"
used in this specification is intended to mean also "light beams" and all
similar beam products of the above mentioned firms and their competitors.
Finally, to complete the description of the present aircraft weighing
apparatuses, reference is made to FIG. 3 by way of example. As seen load
measuring means 10', 11 and 12 are linked operatively to a computer means
CM via an interface I. A readout means R (omitted from FIG. 1 for reasons
of clarity) is linked operatively to the computer means CM along with a
sensor means S in similar manner to that shown for example in
aforementioned U.S. Pat. Nos. 4,639,872 and 4,935,885 which are
incorporated herein by reference. FIG. 3 it will be seen shows
additionally a printer P and a computer mainframe CMF. As will be
understood the applicable additional features disclosed and described in
the aforementioned patents may be utilized in embodiments of the present
invention to enhance their operational abilities.
Before going on to describe the operation of the present invention,
attention is directed to FIG. 4 showing a further embodiment arrangement
300, such comprising load measuring means 10", 11" and 12". Load measuring
means 10", in the case of this particular embodiment example, comprises a
plurality of weigh pads WP being of the type disclosed and described in
McHale et al U.S. Pat. No. 4,935,885 dated Jun. 19, 1990, the weigh WP
being secured within a grid means GM which itself comprises a frame which
is rigidly secured to the aircraft roadway AR. Load measuring means 11"
and 12" are similar one to another, and again are similar to that
disclosed and described in the latter mentioned patent, except that load
measuring means 11" and 12" comprising respective grid means 20' and 21'
are mounted for sliding controlled movement toward and away from one
another upon the aircraft roadway AR. Relative movement of grid means 20'
and 21' with roadway AR is effected by a controllable motor means MM
comprising for example a hydraulic cylinder shown (in dotted line) located
vertically below and beneath respectively grid means 20' and 21'. As will
be understood in this particular embodiment, one end of the hydraulic
cylinder is pivotally connected to the aircraft roadway AR and the other
end of the hydraulic cylinder is pivotally connected to the adjacent grid
means.
Accordingly, controlled operation of the respective motor means MM will
result in the controlled movement in directions of arrows x of load
measuring means 11" and 12" toward and away from one another upon aircraft
roadway AR. A guide means G may be provided to assist the linear movement
of the respective grid means 20' and 21'. In alternative embodiments, grid
means GM may also be mounted for relative sliding movement with aircraft
roadway AR utilising a motor means MM (not shown) mounted and operated in
similar manner as aforedescribed. As will be understood, controlled
movement of grid means GM upon aircraft roadway AR would be linear passing
along center line CL whereby grid means GM moves toward or away from grid
means 20' and 21'. As will be realized, movement of the respective load
measuring means 11" and 12" moves a plurality of weigh pads WP
collectively.
Having reference to FIG. 4A showing arrangement 300A; it shows additional
motor means MM' may be mounted (in vertical spaced relation to motor means
MM) in the aforedescribed manner to provide controlled linear movement of
load measuring means 11" and 12" in the directions of arrows y. To
accommodate this double movement of grid means 20' and 21', extended
mounting rods MP' are also provided in vertical spaced relation to
extended mounting rods MP to permit the necessary "matrix like" sliding of
the grid means 20' and 21' relative to aircraft roadway AR. Rods MP and
MP', as will be realised, are secured to and form part of the grid means.
Arrangements 300 and 300A provide important advantages over the prior art
McHale et al arrangements. Firstly additional aircraft "footprints" are
covered without the need to increase the number of weigh pads WP in a
given grid means or increase the size, i.e. area of the grid means itself.
This is consistent with a stated aim of the present invention. Thus, a
relatively small grid means can serve many extended "footprints". This is
achieved by controlled sliding movement of the grid means 20' and 21' upon
the aircraft roadway AR about the x or y axes or both.
An important feature of the FIG. 4 and FIG. 4A embodiments is that the
motor means MM/MM' for moving the respective grid means 20' and 21' upon
the aircraft roadway AR, is located there beneath. This ensures a smooth
aircraft wheel rolling surface is maintained around the aircraft weigh
station at all times.
An important advantage provided by arrangements 300 and 300A and the like
is that the weigh pads WP can be controllably moved relative the aircraft
wheels to be weighed, thus eliminating the need to reposition the aircraft
and its wheels, i.e. for their aligned reception upon the wheel pads WP.
Other embodiments (not shown) may comprise a single motor means
interconnecting grid means 20' and 21' in a manner similar to that shown
in terms of FIG. 2 interconnecting load measuring means 11 and 12. In such
case grid means 20' and 21' could be guided in their controlled movement
toward and away from one another upon aircraft roadway AR by guide means
G. Again, the single motor means could be positioned below the roadway AR
surface and covered with a metal plate or the like to provide an
uninterrupted road surface in between the respective grid means.
Other embodiments may comprise an arrangement similar to those shown in
FIGS. 4 and 4A wherein grid means 20' and 21' comprise a non-grid frame
supporting centrally thereof a single weigh pad WP. The latter weigh pad
is accordingly moved about the x or y axes or both to suit various
aircraft main undercarriage "footprints". A similar arrangement would
result when the center of the grid means 20' and 21' comprises a weigh pad
and the remainder of the grid means surrounding the weigh pad comprises
non-weighing pads.
Operation of the present invention will now be described.
Referring to FIG. 1, an aircraft to be weighed is moved upon its wheels
comprising for example a nose wheel and main undercarriage wheels depicted
by letters Y and Z. In this instance the nose wheel Y has been steered
along a linear line coincident with axis A and the respective main
undercarriage wheels Z have followed linear paths coincident with the
respective axes L passing centrally through respectively load measuring
means 11 and 12. The latter load measuring means have been prior moved
either manually or by motor means along axis B to the position shown in
FIG. 1 ready to receive the respective aircraft wheels Z. Nose wheel load
measuring means 10 has likewise been moved along axis A in either of the
manners discussed above respective load measuring means 11 and 12 ready to
receive nose wheel Y. The positioning of the aforementioned load measuring
means 10, 11 and 12 has been carried out using either the scale means C, D
and E or computer control using a program accessed by the pilot of the
aircraft or others (using sensor S in conjunction with a transponder means
on the aircraft) from the computer linked to load measuring means 10, 11,
12 (ref. FIG. 3). As will be understood the aforementioned program
includes specifications of the aircraft to be weighed, including wheel
spacing data.
From the wheel positions indicated in FIG. 1, the wheels are moved to
statically rest or dynamically move upon load measuring means 10, 11 and
12 following which the registered wheel loads are shown on readout means
R. The center of gravity is subsequently derived using computer CM, and
also shown on the readout means R. The registered loads and computed
center of gravity data appear on a printout from printer P. Computer
mainframe CMF is simultaneously provided with the registered, recorded and
calculated data.
In a situation where the aircraft has limited space in which to maneuver,
in order to achieve the wheel alignment positions shown in FIG. 1, load
measuring means 10, 11 and 12 are rotated about for example pivot means P1
to assist in obtaining such alignment. The rotation about pivot means P1
may be done manually or by controlled motor means, including motor means
controlled by electronic beam emitted or received via receivers/emitters
E1, E2, E3 and E4, interfacing with similar devices on for example the
nose wheel and main undercarriage structures of the aircraft, an example
of which will now be described and which incidentally may be applied and
adapted for use with the known grid structures disclosed in the
aforementioned '885 patent and others.
With the aircraft wheels not aligned as shown in FIG. 1 respective the
weighing apparatus, a linear electronic beam is for example transmitted
from the nose wheel undercarriage structure of the aircraft to strike
receiver E1 (the path of the beam may be maintained in a direction normal
to the nose wheel axis). The transmitted beam automatically activates
motor means M4 to collectively rotate track-like frame means 19, 20 and 21
carrying load measuring means 10, 11 and 12. With the beam following
rotation of El, rotation continues until the transmitted beam intercepts
receiver E2 whereupon motor means M4 is deactivated and rotation ceases. A
locking system to prevent rotation may be applied. The nose wheel is then
steered along the path of the beam passing coincident with axis A using
well known means and the main undercarriage wheels of the aircraft with
the aid of selective breaking track to the positions shown in FIG. 1, the
aircraft then proceeds to enter upon load measuring means 10, 11 and 12.
Linear electronic beams are emitted from the respective main undercarriage
wheel structures coincident with axis L respectively to strike receivers
E3 and E4 to confirm alignment of the main undercarriage wheels
respectively with load measuring means 11 and 12 as shown in FIG. 1.
Motor means M4, like motor means M2 and M3, is a reversible drive type. One
instance in which this feature is used is when motor means M4 is activated
and drives rotation in a direction opposite to that required for alignment
of the aircraft wheels.
In such instance, rotation continues until for example stop means abutment
24 engages abutment 24' at which time motor means M4 is reversed and
counter rotation continues until the nose wheel emitted beam strikes
receiver E2 to cease rotation and thus provide the desired alignment of
the nose wheel with the respective load measuring means.
In the case of for example a gate location, traffic lights may be used to
assist the pilot in ensuring the wheels of the aircraft are safely placed
on their respective load measuring means. Various other means, including
electronic ones may also be used for this task.
From the foregoing it will be evident that in the case where non-rotatable
load measuring means are used, i.e., where space limitations do not
intrude for maneuvering the aircraft to be weighed, it may be guided
whereby to correctly place its wheels on the pre-positioned load measuring
means, or move its wheels thereover, using the aforementioned electronic
linear beams emitted for example from E2, E3 and E4 interfacing with
transponder means or the like on for example the respective nose and main
undercarriage wheel support structures, with the wheel paths being guided
along respectively axes A and L.
It will be appreciated that the foregoing described operation of activating
operation of motor means M4 by electronic beam means to rotate the load
measuring means applies in principle to the alternative rotating
embodiments, i.e., using motor means M4 or alternatively M2 to rotate the
"turntable" type embodiment or using means M3 to rotate the pendulum type
embodiment, including use of related abutments mentioned above.
From the foregoing it will be evident arrangements 100 and 200 operate in
similar manner in regard to certain aspects.
From the foregoing it will also be evident the various disclosed features
may be substituted one for another to provide a multiplicity of preferred
embodiments to those shown in arrangements 100, 200 and 300, i.e., to suit
not only aircraft of tricycle undercarriage types but also ones of tail
wheel types also others having nose and tail wheel undercarriage
configurations including for example those used on helicopters.
Regarding operation of arrangement 300, the aircraft is positioned for
entry of its wheels upon the respective load weighing means, more
specifically the respective weigh pads WP. As indicated, load measuring
means 11" and 12" and specifically grid means 20" and 21" comprising the
plurality of weigh pads WP can if necessary be moved via operation of the
respective motor means MM to thereby align the weigh pads WP with the main
undercarriage wheels of the aircraft, the nose wheel for example, having
first been positioned to proceed along center line CL. Where no motor
means MM is present, the grid means 20' and 21' would be moved manually
toward and away from one another. In the case of arrangement 300A,
respective motor means MM' are operated to provide further refinement in
terms of positioning grid means 20' and 21' respective the aircraft wheel
positions. Accordingly, motor means MM and MM' are operated to adjust the
weigh pad WP positions if necessary or to position the respective grid
means 20' and 21' for differing aircraft "footprints".
Following advancement of the aircraft to place its wheels upon the
respective weigh pads, the weighing procedure is carried out in similar
manner to that already described.
As indicated previously, other embodiments (not shown) may comprise a
rigidly secured to the roadway single motor means, interconnecting grid
means 20' and 21' in a manner similar to that shown in FIG. 2
interconnecting load measuring means 11 and 12. Thus, operation of the
latter single motor means will move the respective grid means toward or
away from one another as required.
Various changes may be made to the embodiments shown herein without
departing from the scope of the present invention.
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